Apparatus and method for aerodynamic performance enhancement of a wind turbine

ABSTRACT

A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.

BACKGROUND

Embodiments disclosed herein relate generally to apparatus and methodsfor increasing the aerodynamic efficiency of an existing wind turbine.In particular, embodiments disclosed herein relate to apparatus andmethods that enable an acceleration of an airflow into moreaerodynamically efficient region of a wind turbine rotor blade providingan increase in efficiency of an existing wind turbine.

Commonly, rotor blades of wind turbines do not possess an aerodynamicprofile at the inner rotor section. More specifically, the air flow inthe inner rotor portion may pass over the rotor of the wind turbine.Accordingly, root region torque extraction in wind turbines is typicallylow. Thus, not all kinetic energy of the wind passing an area that isswept by the rotor blades is used for the energy production.Accelerating the inboard section velocities and pushing the sped-up flowto outer span locations of the rotor blades will help increase thecoefficient of power (Cp) of the blade.

Accordingly, there is a need for an improved wind turbine that providesfor the acceleration of the flow into and over a more aerodynamicallyefficient region of the rotor blades.

BRIEF SUMMARY

These and other shortcomings of the prior art are addressed by thepresent disclosure, which provides an apparatus and method that enablean acceleration of an airflow into and over a more aerodynamicallyefficient region of a wind turbine rotor blade.

In accordance with an embodiment, provided is an aerodynamic componentfor a wind turbine configured to be mounted to said wind turbine,wherein at least one rotor blade is connected to a hub of said windturbine and defines an inner portion and a profiled outer portion. Theaerodynamic component comprising a front portion configured to bepositioned in front of the inner portion of the at least one rotor bladeof the wind turbine in operation. The aerodynamic component isstructurally configured to: operate in a deployed state to redirect anincoming wind toward the profiled outer portion of the at least onerotor blade; operate in a non-deployed state to allow the incoming windto pass therethrough toward the inner portion of the at least one rotorblade; and allow rotation of the at least one rotor blade about itslongitudinal axis for pitch angle adjustment of the at least one rotorblade without interfering with the deployment of the aerodynamiccomponent.

In accordance with another embodiment, provided is a wind turbinecomprising: a hub; at least one rotor blade connected to the hub; and adeployable aerodynamic component configured to be mounted to the windturbine. The deployable aerodynamic component comprising: a frontportion configured to be positioned in front of the inner portion of theat least one rotor blade of the wind turbine in operation; wherein thedeployable aerodynamic component is structurally configured to: operatein a deployed state to redirect an incoming wind toward the profiledouter portion of the at least one rotor blade; operate in a non-deployedstate to allow the incoming wind to pass therethrough toward the innerportion of the at least one rotor blade; and allow rotation of the atleast one rotor blade about its longitudinal axis for pitch angleadjustment of the at least one rotor blade without interfering with thedeployment of the aerodynamic component. The rotor blade comprising aninner portion and a profiled outer portion.

In accordance with yet another embodiment, provided is a method foraerodynamic performance enhancement of a wind turbine comprising:providing a wind turbine including a hub and at least one rotor bladeconnected to the hub; mounting a deployable aerodynamic component to thewind turbine; determining the presence of winds exceeding presetparameters; deploying the deployable aerodynamic component to redirectan incoming wind toward the profiled outer portion of the at least onerotor blade when winds do not exceed the present parameters andoperating the deployable aerodynamic component in a non-deployed stateto allow the incoming wind to pass therethrough toward the inner portionof the at least one rotor blade when winds exceed the presentparameters; and rotating the at least one rotor blade about itslongitudinal axis to generate energy. The at least one rotor bladehaving an inner portion and a profiled outer portion

Other objects and advantages of the present disclosure will becomeapparent upon reading the following detailed description and theappended claims with reference to the accompanying drawings.

BRIEF DESCRIPTION OF THE FIGURES

The above and other features, aspects, and advantages of the presentdisclosure will become better understood when the following detaileddescription is read with reference to the accompanying drawings in whichlike characters represent like parts throughout the drawings, wherein

FIG. 1 is schematic side view of a wind turbine including a deployableaerodynamic component in a deployed state according to an embodiment;

FIG. 2 is an enlarged schematic side view of the wind turbine includingthe deployable aerodynamic component of FIG. 1 in a deployed state;

FIG. 3 is perspective view of the wind turbine including the deployableaerodynamic component of FIG. 1 in a non-deployed state;

FIG. 4 is a perspective view the wind turbine including the deployableaerodynamic component underlying structure of FIG. 1;

FIG. 5 is a side view of a wind turbine including a deployableaerodynamic component in a deployed state according to an embodiment;

FIG. 6 is a front view of the wind turbine including the deployableaerodynamic component of FIG. 5;

FIG. 7 is a perspective view of the wind turbine including thedeployable aerodynamic component of FIG. 5 in a partially non-deployedstate;

FIG. 8 is a side view of a wind turbine including a deployableaerodynamic component in a deployed state according to an embodiment;

FIG. 9 is a front view of the wind turbine including the deployableaerodynamic component of FIG. 8 in a deployed state;

FIG. 10 is a side view of the wind turbine including the deployableaerodynamic component of FIG. 8 in a non-deployed state;

FIG. 11 is a front view of the wind turbine including the deployableaerodynamic component of FIG. 8 in a non-deployed state;

FIG. 12 is a side view of a wind turbine including a deployableaerodynamic component according to an embodiment in a deployed state;

FIG. 13 is a front view of the wind turbine including the deployableaerodynamic component of FIG. 12 in a deployed state;

FIG. 14 is a side view of a wind turbine including a deployableaerodynamic component of FIG. 12 in a non-deployed state;

FIG. 15 is a front view of the wind turbine including the deployableaerodynamic component of FIG. 12 in a non-deployed state;

FIG. 16 is a front view of a wind turbine including a deployableaerodynamic component according to an embodiment in a deployed state;

FIG. 17 is a side view of the wind turbine including the deployableaerodynamic component of FIG. 16 in a deployed state;

FIG. 18 is a front view of a wind turbine including a deployableaerodynamic component in a deployed state according to an embodiment;

FIG. 19 is a side view of the wind turbine including the deployableaerodynamic component of FIG. 18 in a deployed state;

FIG. 20 is a side view of the wind turbine including the deployableaerodynamic component of FIG. 18 in a non-deployed state;

FIG. 21 shows a side view of a wind turbine including a deployableaerodynamic component in a deployed state according to an embodiment;

FIG. 22 is a front view of the wind turbine including the deployableaerodynamic component of FIG. 21 in a deployed state;

FIG. 23 is a side view of the wind turbine including the deployableaerodynamic component of FIG. 21 in a non-deployed state;

FIG. 24 is a front view of the wind turbine including the deployableaerodynamic component of FIG. 21 in a non-deployed state;

FIG. 25 is a front view of the wind turbine including the deployableaerodynamic component in a deployed state according to an embodiment;

FIG. 26 is a front view of the wind turbine including the deployableaerodynamic component of FIG. 25 in a non-deployed state;

FIG. 27 is a front view of a wind turbine including a deployableaerodynamic component in a deployed state according to an embodiment;

FIG. 28 is a front view of the wind turbine including the deployableaerodynamic component of FIG. 27 in a non-deployed state;

FIG. 29 is a front view of a wind turbine including a deployableaerodynamic component in a non-deployed state according to anembodiment; and

FIG. 30 is a schematic block diagram of method for aerodynamicperformance enhancement of a wind turbine according to an exemplaryembodiment.

DETAILED DESCRIPTION

The invention will be described for the purposes of illustration only inconnection with certain embodiments; however, it is to be understoodthat other objects and advantages of the present disclosure will be madeapparent by the following description of the drawings according to thedisclosure. While preferred embodiments are disclosed, they are notintended to be limiting. Rather, the general principles set forth hereinare considered to be merely illustrative of the scope of the presentdisclosure and it is to be further understood that numerous changes maybe made without straying from the scope of the present disclosure.

Reference will now be made in detail to the various embodiments of theinvention, one or more examples of which are illustrated in the figures.Each example is provided by way of explanation of the invention, and isnot meant as a limitation of the invention. For example, featuresillustrated or described as part of one embodiment can be used on or inconjunction with other embodiments to yield yet a further embodiment. Itis intended that the present invention includes such modifications andvariations.

FIG. 1 shows a wind turbine 100. The wind turbine 100 includes a tower102 onto which a nacelle 104 is arranged. Within the nacelle 104 agenerator (not shown) for producing electrical current is placed. Thegenerator is connected to a hub 106 with a substantial horizontal shaft.A plurality of rotor blades 108 are coupled to the hub 106 andconfigured to rotate about an axis (horizontal or vertical) at a ratedetermined by the wind speed and the shape of the rotor blades 108.Typically the plurality of rotor blades 108 includes two or more rotorblades. The rotor blades 108 and the hub 106 form a rotor 110 of thewind turbine 100. In operation the wind, indicated by arrows 112,imparts a rotation on the rotor 110 due to an aerodynamic profile on therotor blades 108. More specifically, in the illustrated embodiment, therotor 110 turns around a substantially horizontal rotor axis 114, whichis substantially parallel to the wind direction 112. The rotor 110drives the generator, such that electrical energy is produced from thekinetic energy of the wind 112.

It should be noted that relative adjectives like in front, backward,behind and rear are defined with respect to the wind direction 112related to a wind turbine 100 in operation, i.e. when the wind turbine100 produces electrical energy. That means that the wind 112 flows froma front end 116 to a back end 118 of the wind turbine 100. In addition,the terms axial or radial relate to the rotor axis 114 of the hub 106,when the wind turbine 100 produces electrical energy. Thus, as describedabove, the rotor axis 114 is substantially parallel to the wind 112direction.

Referring again to the drawings wherein, as previously stated, identicalreference numerals denote the same elements throughout the variousviews, FIGS. 2-4 depict in simplified schematic drawings, a wind turbineaccording to an embodiment. For the sake of simplicity, only a portionof the plurality of rotor blades 108 is shown. Each of the plurality ofrotor blades 108 has an outer portion 122 and an inner portion 124. Theterms “outer” and “inner” are used with respect to the hub 106.Therefore, the outer portion 122 of each of the plurality of rotorblades 108 is radially outside of the inner portion 124 in FIG. 2. Theinner portion 124 of each of the plurality of rotor blades 108 isconnected to the hub 106. Each rotor blade 108 may be, in a typicalembodiment, turned around its longitudinal axis to adjust a pitch angle.For that purpose a pitch mechanism is located in the hub 106 and/or thenacelle 104 of the wind turbine 100. The outer portion 122 of each ofthe rotor blades 108 has a wing shaped profile, such that the outerportion may also be called profiled section or profiled outer portion122 of the rotor blade 108. The front end of each of the plurality ofrotor blades 108 is typically straight from the connection to the hub tothe outer portion 122; in another typical embodiment of the presentpatent application the front end of each of the plurality of rotorblades 108 is typically straight to the blade tip of each of the rotorblades 108. Thus, a leading edge 126, i.e. the windward or front edge ofeach of the plurality of rotor blades 108, defines during operation ofthe wind turbine 100, i.e. when the hub 106 and the rotor blades 108turn around the rotor axis 114, a substantially flat disk. Thus, theouter end of the inner portion 124, approximately where the profiledportion begins, i.e. where each of the rotor blades 108 start theleeward protrusion in the embodiment shown in FIG. 2 when looking from ahub sided end of the rotor blade 108 to the blade tip, is defining acircle around the rotor axis 114.

As illustrated in FIG. 2, in front, i.e. windward, of the rotor blades108, a deployable aerodynamic component 130 according to an embodimentis symmetrically disposed with respect to the turning axis 114. In theillustrated embodiment, the deployable aerodynamic component 130resembles an umbrella-like structure, and is thus referred to herein asan umbrella-like deployable aerodynamic component 132. The umbrella-likedeployable aerodynamic component 132 defining a front portion 152 and arear portion 154, and including a mechanically deployable supportstructure (described presently) and a skin-like covering 134. Theskin-like covering may be comprised of a tensionable fabric, plastic, orany other suitable material capable of creating a flow blockage andredirecting the incoming wind 112 as described herein.

The umbrella-like deployable aerodynamic component 132 may be connectedto the hub 106 via a shaft 136, or later connected to an existing smallspinner (not shown) already mounted on the hub of the wind turbine 100.In the last case, the deployable aerodynamic component 130 covers thesmall spinner. Thus, the deployable aerodynamic component 130 may be anose cone of the hub 106. The umbrella-like deployable aerodynamiccomponent 132 is in a typical embodiment symmetrically placed withrespect to the turning axis 114 when mounted on a wind turbine 100. Theumbrella-like deployable aerodynamic component 132 when deployed mayhave a parabolic or semi-spherical outer shape as illustrated in FIG. 2,or any other shape capable of redirecting the airflow as indicatedherein when deployed. When deployed, the umbrella-like deployableaerodynamic component 132 guides or redirects incoming wind 112 that istypically directed toward the hub 106 or to the nacelle 104 toward theprofiled or outer portions 122 of each of the plurality of rotor blade140. Thus, kinetic energy of the wind 112 directed toward the hub 106 isalso capable of being transformed it to electrical energy.

In an embodiment, the umbrella-like deployable aerodynamic component 132has a maximum outer diameter D in front of the rotor blades 108 that iscorresponding substantially to a diameter of the circle defined by theouter end of the inner portion 124 in operation of the wind turbine 100.The maximum outer diameter D might also be slightly greater or smallerthan the circle. Hence, the wind 112 directed to the hub 106 and thenacelle 1104 is directed along the umbrella-like deployable aerodynamiccomponent 132 to the outer portion 122 of the rotor blades 108, asindicated by arrows 112. The aerodynamic shape of the umbrella-likedeployable aerodynamic component 132 causes an acceleration in the flowof wind 112 over the more aerodynamically efficient regions of each ofthe plurality of blades 108.

FIG. 3 illustrates in a simplified schematic the deployable aerodynamiccomponent 130, and more particularly the umbrella-like deployableaerodynamic component 132, when in a non-deployed state. Moreparticularly, during a high wind occurrence, when loading/drag or thrustloads become too great for the umbrella-like deployable aerodynamiccomponent 132 to withstand, the structure may be retracted to anon-deployed state. In an embodiment, the non-deployed state of theumbrella-like deployable aerodynamic component 132 resembles a typicalumbrella-like folded structure as best illustrated in FIG. 3. Theaerodynamic shape of the umbrella-like deployable aerodynamic component132 when in the non-deployed state minimizes any blockage or redirectingof the flow of wind 112 and allows the wind 112 to flow toward theplurality of blades 108 as is typical. In an alternate embodiment, theskin-like structure 134 may be configured to detach from an underlyingstructure without an immediate requirement to retract the underlyingstructure.

The underlying structure for the umbrella-like deployable aerodynamiccomponent 132 is best illustrated in FIG. 4. More particularly,illustrated is a support structure 138 for the umbrella-like deployableaerodynamic component 132 of FIGS. 2 and 3. The support structure 138 isillustrated having the skin-like covering 134 (FIG. 3) removed forsimplicity of illustrating the support structure 138. In an embodiment,the support structure 138 is coupled to the shaft 136, or alternativelycoupled to the hub 106 via an alternate means, such as a primaryextension tube 140 configured as a part of the support structure 138. Inan embodiment, the support structure 138 is further comprised of asecondary extension tube 142, a plurality of spreaders 144 configured toprovide immediate support to the skin-like covering 134 and a pluralityof secondary supports 146. The secondary extension tube 142 is slideablycoupled to the primary extension tube 140 so as to provide adjustment ofa clearance space between the umbrella-like deployable aerodynamiccomponent 132 and the hub 106. The plurality of secondary supports 146are coupled to the plurality of spreaders 144 and a support structurehub 150 through which the primary and secondary extension tubes 140, 142extend. In an embodiment, a plurality of power heads 148 are providedproximate the support structure hub 150. The plurality of power heads148 may provide slideable movement of the support structure hub 150, ina forward and aft direction, along the primary and/or the secondarytubes 140, 142, thus enabling deployment and retraction of theumbrella-like deployable aerodynamic component 132.

Referring now to FIGS. 5-7, in which like features are designated withthe same reference numbers, illustrated is another embodiment of thedeployable aerodynamic component 130 coupled to a wind turbine 100. Thedeployable aerodynamic component 130 according to FIGS. 5-7 isconfigured as a roller and support arc deployable aerodynamic component160, and has a generally similar shape as the umbrella-like structurepreviously disclosed. In this particular embodiment, and as bestillustrated in FIG. 5, the roller and support arc deployable aerodynamiccomponent 160 is coupled to the wind turbine 100, and more particularlythe hub 106 of the wind turbine 100, via a shaft 136, and defining afront portion 162 and a rear portion 164. The roller and support arcdeployable aerodynamic component 160 when deployed is shaped similar tothe deployable aerodynamic component 130, and more particularly theumbrella-like deployable aerodynamic component 132, described withrespect to FIGS. 2-4. FIG. 6 shows a front view of an embodiment of theroller and support arc deployable aerodynamic component 160 with asubstantially circular shape in a front view when in a deployed state.The roller and support arc deployable aerodynamic component 160 may havein this case a paraboloid shaped form or a form of a sphere segment whenviewed in a side view. As it is shown in this embodiment, the innerportions 124 of each of the plurality of rotor blade 108 are completelycovered in wind direction 112 when deployed. In some embodiments, only asubstantial portion of the inner portions 124 might be covered by theroller and support arc deployable aerodynamic component 160 in directionof the wind 112. A substantial portion of the inner portion may be 50 to100 percent, 75 to 100 percent, or 90 to 100 percent of a total lengthof the inner portion 124. The total length of the inner portion 124 istypically the distance from a connecting flange for connecting each ofthe rotor blades 108 to the hub 106 to the beginning of the airfoiled orprofiled outer portion 122 of the rotor blade 108. In an embodiment, theroller and support arc deployable aerodynamic component 160 may have amaximal outer diameter D of about the diameter of the circle defined bythe outer end of the inner portion 124 in operation of the wind turbine100.

The rear portion 164 of the deployable aerodynamic component 130, andmore particularly the roller and support arc deployable aerodynamiccomponent 160 may have a substantially circular shape defined by a frame168, about which a plurality of support arcs 170, each having a roller172 coupled thereto the support arc 170 and the frame 168, are moveable.In an embodiment, the rear portion 164 may at least partially enclosethe hub 106 of the wind turbine. The rear portion 164 of the roller andsupport arc deployable aerodynamic component 160 is formed such that theairfoiled shaped outer portion 122 of each of the plurality of rotorblades 108 is not touching in any pitch angle of the rotor blade 108 therear portion 164 of the deployable aerodynamic component 130 Therefore,the deployable aerodynamic component 130 is adapted to provide a low airresistance and to guide the wind 112 toward the airfoiled shaped outerportion 122 of the rotor blades 108 when deployed.

The roller and support arc deployable aerodynamic component 160 furtherincludes a skin-like covering 134, such as a tensionable fabric,supported by support arcs 170. In an embodiment, the skin-like covering134 is configured to overlay the support arcs 170 and being coupledthereto to allow for deployment. In an alternate embodiment, theskin-like covering 134 is configured to extend between adjacent supportarcs 170, being coupled thereto. The roller and support arc deployableaerodynamic component 160 is deployable via mechanical automation thatprovides for movement of the support arcs 170, via rollers 172, aboutthe frame 168. When deployed, the roller and support arc deployableaerodynamic component 160 provides blockage and redirecting of theincoming wind 112 toward the outer portions 122 of each of the pluralityof rotor blades 108, previously described. In addition, the aerodynamicshape of roller and support arc deployable aerodynamic component 160causes an acceleration in the flow of wind 112 over the moreaerodynamically efficient regions of each of the plurality of blades108.

FIG. 7 illustrates in a simplified schematic view roller and support arcdeployable aerodynamic component 160 during the process of deployment asthe rollers 172 move about the frame 168. In a non-deployed state, suchas during a high wind occurrence, when loading/drag or thrust loadsbecome too great for roller and support arc deployable aerodynamiccomponent 160 to withstand, the support arcs 170 may be moved about theframe 168 so as to stack one against another, and configured in anon-deployed state. The aerodynamic shape of roller and support arcdeployable aerodynamic component 160 when in the non-deployed statedminimizes any blockage or redirecting of the flow of wind 112 and allowsthe wind 112 to flow toward the inner portion 124 of the plurality ofblades 108 as is typical. In an alternate embodiment, the skin-likestructure may be configured to detach from an underlying structurewithout an immediate requirement to move the support arcs 170 about theframe 168.

Referring now to FIGS. 8-11, in which like features are designated withthe same reference numbers, illustrated is another embodiment of thedeployable aerodynamic component 130 coupled to a wind turbine 100. Moreparticularly, illustrated in FIGS. 8 and 9 is another embodiment of thedeployable aerodynamic component 130 in a deployed stated, andillustrated in FIGS. 10-11 in a non-deployed state. The deployableaerodynamic component 130 according to FIGS. 8-11 is configured as aweighted cable deployable aerodynamic component 180, and when deployedhas a shape generally similar to the umbrella-like aerodynamic component132 structure previously disclosed, but in contrast is based on aspinning action of the component 180 to deploy and take shape. In thisparticular embodiment, and as best illustrated in FIG. 8, the weightedcable deployable aerodynamic component 180 is coupled to the windturbine 100, and more particularly the hub 106 of the wind turbine 100,via a shaft 136, and includes a front portion 182 and a rear portion184. The weighted cable deployable aerodynamic component 180 whendeployed is shaped similar to the deployable aerodynamic component 130,and more particularly the umbrella-like deployable aerodynamic component132, described with respect to FIGS. 2-4. Therefore, it may have adeployed shape of a substantially spherical segment or a substantiallyparaboloid shape when viewed from a side, with a maximal outer diameterD of about a diameter of the circle defined by the outer end of theinner portion 124 in operation of the wind turbine 100.

The weighted cable deployable aerodynamic component 180 generallyincludes a plurality of cables 186, each having a first end extendingfrom a central component 188 at a front portion 182 to a second endproximate the rear portion 184 onto which a weight 190 is coupled. Askin-like covering 134, such as a tensionable fabric is supported by thecables 186. In an embodiment, the skin-like covering 134 is coupledthereto to plurality of cables 186 to allow for deployment. In analternate embodiment, the skin-like covering 134 is configured to extendbetween adjacent cables 186, being coupled thereto. In an alternateembodiment, the skin-like covering 134 may extend over the cables 134,being coupled thereto. During deployment, the rear portion 184 may havea substantially circular shape dependent upon a length “L” of each cable186. In a preferred embodiment, the length “L” is the same for each ofthe plurality of cables 186. The rear portion 184 of the weighted cabledeployable aerodynamic component 180 is formed such that the airfoiledshaped outer portion 122 of each of the plurality of rotor blades 108 isnot touching in any pitch angle of the rotor blade 108 the rear portion164 of the weighted cable deployable aerodynamic component 180.Therefore, the weighted cable deployable aerodynamic component 180 isadapted to provide a low air resistance and to guide the wind 112 towardthe airfoiled shaped outer portion 122 of the rotor blades 108 whendeployed.

The weighted cable deployable aerodynamic component 180 is deployablevia mechanical automation that provides for a spinning action of thecentral component 188. The spinning action, as indicated in FIG. 9,creates a dynamic structure in front of the plurality of rotor blades108 due to centrifugal force. When deployed, the weighted cabledeployable aerodynamic component 180 provides blockage and redirectingof the incoming wind 112 toward the outer portions 122 of each of theplurality of rotor blades 108, previously described. In addition, theaerodynamic shape of the weighted cable deployable aerodynamic component180 causes an acceleration in the flow of wind 112 over the moreaerodynamically efficient regions of each of the plurality of blades108.

FIGS. 8 and 9 illustrate in a simplified schematic view the weightedcable deployable aerodynamic component 180 when deployed. In anon-deployed state as illustrated in FIGS. 10 and 11, such as during ahigh wind occurrence, when loading/drag or thrust loads become too greatfor the weighted cable deployable aerodynamic component 180 towithstand, the spinning action of the central component 188 is stoppedand thus the weighted second ends of the cables 186 close about thecentral shaft 136 to a non-deployed state. In an embodiment, additionalcables or means of control may be attached to the second ends of thecables 186, and more particularly each of the weights 190 and to therotor hub 106 or shaft 136 for additional control during deployment andnon-deployment. The aerodynamic shape of the weighted cable deployableaerodynamic component 180 when in the non-deployed stated minimizes anyblockage or redirecting of the flow of wind 112 and allows the wind 112to flow toward the inner portion 124 of the plurality of blades 108 asis typical. In an alternate embodiment, the skin-like structure may beconfigured to detach from each of the plurality of cables 186 without animmediate requirement to stop the spinning action of the centralcomponent 188.

Referring now to FIGS. 12-15, in which like features are designated withthe same reference numbers, illustrated is another embodiment of thedeployable aerodynamic component 130 coupled to a wind turbine 100. Moreparticularly, illustrated in FIGS. 12 and 13 is another embodiment ofthe deployable aerodynamic component 130 in a deployed stated, andillustrated in FIGS. 14 and 15 in a non-deployed state. The deployableaerodynamic component 130 according to FIGS. 12-15 is configured as afluid deployable aerodynamic component 200, and more particularlyconfigured for deployment by inflating with a fluid, such as air. Inthis particular embodiment, and as best illustrated in FIG. 12, thefluid deployable aerodynamic component 200 is coupled to the windturbine 100, and more particularly the hub 106 of the wind turbine 100,via a shaft 136, and includes a front portion 202 and a rear portion204. The fluid deployable aerodynamic component 200 when deployed takeson a dome-like shape as best illustrated in FIG. 12. Therefore, it mayhave a deployed shape of a substantially spherical segment or asubstantially paraboloid shape with a maximal outer diameter D of aboutthe diameter of a circle defined by the outer end of the inner portion124 in operation of the wind turbine 100.

The fluid deployable aerodynamic component 200 generally includes askin-like covering 134, such as a fabric that is configured to beinflated with a fluid, such as air. In an embodiment, the skin-likecovering 134 is coupled thereto at least one of the hub 106 or shaft 136to allow for deployment and positioning relative to the wind turbine100. Included is a means for providing inflation (not shown) to thefluid deployable aerodynamic component 200. During deployment, the rearportion 204 may have a substantially circular shape when viewed in frontview. The rear portion 204 of the fluid deployable aerodynamic component200 is formed such that the airfoiled shaped outer portion 122 of eachof the plurality of rotor blades 108 is not touching in any pitch angleof the rotor blade 108 the rear portion 204 of the fluid deployableaerodynamic component 200. Therefore, the fluid deployable aerodynamiccomponent 200 is adapted to provide a low air resistance and to guidethe wind 112 toward the airfoiled shaped outer portion 122 of the rotorblades 108 when deployed.

The fluid deployable aerodynamic component 200 is deployable viamechanical automation that provides for inflation of the skin-likecovering 134. The inflation of the fluid deployable aerodynamiccomponent 200, as illustrated in FIGS. 12 and 13, creates a dynamicstructure in front of the plurality of rotor blades 108. When deployed,the fluid deployable aerodynamic component 200 provides blockage andredirecting of the incoming wind 112 toward the outer portions 122 ofeach of the plurality of rotor blades 108, previously described. Inaddition, the aerodynamic shape of the fluid deployable aerodynamiccomponent 200 causes an acceleration in the flow of wind 112 over themore aerodynamically efficient regions of each of the plurality ofblades 108.

In a non-deployed state as illustrated in FIGS. 14 and 15, such asduring a high wind occurrence, when loading/drag or thrust loads becometoo great for the fluid deployable aerodynamic component 200 towithstand, the skin-like covering 134 is deflated, and may be packedaway in a manner generally similar to a parachute. The aerodynamic shapeof the fluid deployable aerodynamic component 200 when in thenon-deployed stated minimizes any blockage or redirecting of the flow ofwind 112 and allows the wind 112 to flow toward the inner portion 124 ofthe plurality of blades 108 as is typical. In an alternate embodiment,the skin-like structure may be configured to detach from the windturbine 100 without an immediate requirement to deflate the skin-likecovering 134 and pack it away.

Referring now to FIGS. 16 and 17, in which like features are designatedwith the same reference numbers, illustrated is another embodiment ofthe deployable aerodynamic component 130 coupled to a wind turbine, suchas the wind turbine 100 of FIG. 1. More particularly, illustrated inFIGS. 16 and 17 is another embodiment of the deployable aerodynamiccomponent 130 in a deployed state. The deployable aerodynamic component130 according to FIGS. 16 and 17 is configured as a perimeter paneleddeployable aerodynamic component 210, and more particularly configuredfor deployment by rotating a plurality of panels 216 positioned about aperimeter 214 of the component 210 in a manner to redirect an incomingwind 112. In this particular embodiment, the perimeter paneleddeployable aerodynamic component 210 is coupled to the wind turbine, andmore particularly the hub 106 of the wind turbine 100, via a shaft 136,and includes a front portion 212. In an embodiment the perimeter paneleddeployable aerodynamic component 210 is configured having asubstantially dome-like shape with an optional central opening 218formed therethrough. The perimeter paneled deployable aerodynamiccomponent 210 may have a deployed shape of a substantially sphericalsegment or a substantially paraboloid shape with a maximal outerdiameter of about the diameter of a circle defined by the outer end ofthe inner portion 124 in operation of the wind turbine 100.

The perimeter paneled deployable aerodynamic component 210 generallyincludes the plurality of panels 216 spaced about a perimeter 214 of thecomponent 210 and configured to rotate during deployment via a pluralityof rotation arms 220 coupled to each of the rotating panels 216 at afirst end with a plurality of couplings 222, and to a means forproviding rotation 224 as a second end. The component 210 may furtherinclude a plurality of secondary rotation arms 226 each coupled at afirst end to a panel 216 and to the hub 106 at a second end. In anembodiment, the plurality of secondary rotation arms 226 are provided asan additional support structure to the rotating panels 216 and may beconfigured to aid in rotation of the rotating panels 216 or simplyprovide additional support.

The perimeter paneled deployable aerodynamic component 210 is configuredsuch that the airfoiled shaped outer portion 122 (FIG. 1) of each of theplurality of rotor blades 108 (FIG. 1) is not touching the panels 216 ofthe perimeter paneled deployable aerodynamic component 210 in any pitchangle of the rotor blade 108. During deployment, the panels 216 arerotated via rotation arms 220 and the means for providing rotation 224in a manner to guide the wind 112 toward the airfoiled shaped outerportion 122 of the rotor blades 108.

As previously indicated, the perimeter paneled deployable aerodynamiccomponent 210 is deployable via mechanical automation that provides forrotation of the panels 216 relative to the incoming wind 112. Therotation of the panels 216, as illustrated in FIGS. 16 and 17, so as tobe oriented substantially perpendicular to the direction of the incomingwind 112, creates a dynamic structure in front of the plurality of rotorblades 108. When deployed, the perimeter paneled deployable aerodynamiccomponent 210 provides blockage and redirecting of the incoming wind 112toward the outer portions 122 of each of the plurality of rotor blades108, as previously described. In addition, the aerodynamic shape of theperimeter paneled deployable aerodynamic component 210 causes anacceleration in the flow of wind 112 over the more aerodynamicallyefficient regions of each of the plurality of blades 108.

In a non-deployed state, such as during a high wind occurrence, whenloading/drag or thrust loads become too great for the perimeter paneleddeployable aerodynamic component 210 to withstand, the panels 216 arerotated by the rotation arms 220 and the means for providing rotation224 in a direction substantially parallel (not shown) to a direction ofan incoming wind 112. The aerodynamics of the perimeter paneleddeployable aerodynamic component 210 when in the non-deployed statedminimizes any blockage or redirecting of the flow of wind 112 and allowsthe wind 112 to flow toward the inner portion 124 of the plurality ofblades 108 as is typical.

Referring now to FIGS. 18-20, in which like features are designated withthe same reference numbers, illustrated is another embodiment of thedeployable aerodynamic component 130 coupled to a wind turbine 100. Moreparticularly, illustrated in FIGS. 18 and 19 is another embodiment ofthe deployable aerodynamic component 130 in a deployed state, andillustrated in FIG. 20 in a non-deployed state. The deployableaerodynamic component 130 according to FIGS. 18-20 is configured as apaneled deployable aerodynamic component 230, generally similar to theperimeter paneled deployable aerodynamic component 210 of FIGS. 15-17,but having a different panel configuration. More particularly, thepaneled deployable aerodynamic component 230 is configured having aplurality of panels 236 formed in a front portion 232 of the paneleddeployable aerodynamic component 230, in contrast to the perimeterconfiguration as in the previous embodiment. Although the paneleddeployable aerodynamic component 230 is illustrated having four panels236, it should be understood that the component 230 may be configured toinclude any number of panels 236 dependent upon design parameters. It isanticipated that at least two panels 236 are required.

The paneled deployable aerodynamic component 230 is configured fordeployment by rotating the plurality of panels 216 of the component 210in a manner to redirect an incoming wind 112 as illustrated in FIG. 19.In this particular embodiment, the paneled deployable aerodynamiccomponent 230 is coupled to the wind turbine 100, and more particularlythe hub 106 of the wind turbine 100, via a shaft 136, and includes thefront portion 232. In an embodiment the paneled deployable aerodynamiccomponent 230 is configured having a substantially dome-like shape.Although the paneled deployable aerodynamic component 230 is notdepicted as including a central opening, such as central opening 218 ofthe previous embodiment illustrated in FIGS. 16 and 17, it may beincluded. The paneled deployable aerodynamic component 230 may have ageneral shape of a substantially spherical segment or a substantiallyparaboloid shape when viewed from a side with a maximal outer diameter Dof about the diameter of a circle defined by the outer end of the innerportion 124 in operation of the wind turbine 100.

The paneled deployable aerodynamic component 230 generally includes theplurality of panels 236 spaced evenly over the front portion 232 of thecomponent 210 and configured to rotate during deployment via a means forproviding rotation 244 coupled to each of the rotating panels 236 via arotation arm 240. In an embodiment, the panels 236 are configured torotate in a manner similar to that previous described with regard toFIGS. 15-17. The paneled deployable aerodynamic component 230 isconfigured such that the airfoiled shaped outer portion 122 of each ofthe plurality of rotor blades 108 is not touching in any pitch angle ofthe rotor blade 108, the panels 236 of the paneled deployableaerodynamic component 230. During deployment, the panels 236 are rotatedin a manner to guide the wind 112 toward the airfoiled shaped outerportion 122 of the rotor blades 108 as illustrated in FIG. 19.

The paneled deployable aerodynamic component 230 is deployable viamechanical automation that provides for rotation of the panels 236relative to the incoming wind 112. The rotation of the panels 216, asillustrated in FIGS. 18 and 19 substantially perpendicular to thedirection of the incoming wind 112, creates a dynamic structure in frontof the plurality of rotor blades 108. When deployed, the paneleddeployable aerodynamic component 230 provides blockage and redirectingof the incoming wind 112 toward the outer portions 122 of each of theplurality of rotor blades 108, previously described. In addition, theaerodynamic shape of the paneled deployable aerodynamic component 230causes an acceleration in the flow of wind 112 over the moreaerodynamically efficient regions of each of the plurality of blades108.

In a non-deployed state, such as during a high wind occurrence, whenloading/drag or thrust loads become too great for the paneled deployableaerodynamic component 230 to withstand, the panels 236 are rotated in adirection substantially parallel to a direction of an incoming wind 112,such as illustrated in FIG. 20. The aerodynamics of the paneleddeployable aerodynamic component 230 when in the non-deployed statedminimizes any blockage or redirecting of the flow of wind 112 and allowsthe wind 112 to flow toward the inner portion 124 of the plurality ofblades 108 as is typical.

FIGS. 21-24, in which like features are designated with the samereference numbers, illustrate another embodiment of the deployableaerodynamic component 130 coupled to a wind turbine 100. Moreparticularly, illustrated in FIGS. 21 and 22 is another embodiment ofthe deployable aerodynamic component 130 in a deployed state, andillustrated in FIGS. 23 and 24 in a non-deployed state. The deployableaerodynamic component 130 according to FIGS. 21-24 is configured as arotor flap deployable aerodynamic component 250. More particularly, therotor flap deployable aerodynamic component 250 is configured having aplurality of rotor flaps or panels 256 that retract or fold away duringnon-deployment. Although the rotor flap deployable aerodynamic component250 is illustrated having a specific number of rotor flaps 256, itshould be understood that the component 250 may be configured to includeany number of rotor flaps 256 dependent upon design parameters. It isanticipated that the rotor flaps 256 are configured in alignment witheach of the plurality of rotor blades 108 as illustrated and may fold orretract into each of said rotor blades 108.

The rotor flap deployable aerodynamic component 250 is configured fordeployment by an actuation mechanism (not shown) utilizing hydraulics,levers, or the like to unfold or extend the plurality of rotor flaps 256of the component 250 in a manner to redirect an incoming wind 112impinging on a front portion 252 as illustrated in FIGS. 21 and 22. Inthis particular embodiment, the rotor flap deployable aerodynamiccomponent 250 is coupled to the wind turbine 100, and more particularlythe hub 106 of the wind turbine 100, via a shaft 136. In an embodimentthe rotor flap deployable aerodynamic component 250, and moreparticularly each of the rotor flaps 256, is configured having asubstantially delta-like shape relevant to each rotor blade 108 during adeployed state. In an embodiment the rotor flap deployable aerodynamiccomponent 250, and more particularly the front portion 252 may have ageneral shape of a substantially spherical segment or a substantiallyparaboloid shape with a maximal outer diameter D of about the diameterof a circle defined by the outer end of the inner portion 124 inoperation of the wind turbine 100 when in a deployed state.

The rotor flap deployable aerodynamic component 250 generally includesthe plurality of rotor flaps 256 spaced having a maximal outer diameterD of about the diameter of a circle defined by the outer end of theinner portion 124 of the wind turbine 100. The rotor flaps 256 areconfigured to extend or unfold during deployment via hydraulics, levers,or other means for accomplishing such. In an embodiment, the rotor flaps256 are configured such that the airfoiled shaped outer portion 122 ofeach of the plurality of rotor blades 108 is not touching in any pitchangle of the rotor blade 108, the rotor flaps 256 of the paneleddeployable aerodynamic component 250. During deployment, the rotor flaps256 are deployed in a manner to guide the wind 112 toward the airfoiledshaped outer portion 122 of the rotor blades 108 as illustrated in FIGS.21 and 22. In an embodiment, it is anticipated that the plurality ofrotor flaps 108 may be configured having a “shroud-like” shape to directthe incoming wind 112 in an upward and outward direction toward theairfoiled shaped outer portion 122 of the rotor blades 108.

The rotor flap deployable aerodynamic component 250 is deployable viamechanical automation that provides for extension of the rotor flaps 256relative to the rotor blades 108. The extending of the rotor flaps 256,as illustrated in FIGS. 21 and 22, from a centerline of each of therotor blades 108, creates a dynamic structure in front of each of theplurality of rotor blades 108. When deployed, the rotor flap deployableaerodynamic component 250 provides blockage and redirecting of theincoming wind 112 toward the outer portions 122 of each of the pluralityof rotor blades 108, as previously described. In addition, theaerodynamic shape of the rotor flap deployable aerodynamic component 250causes an acceleration in the flow of wind 112 over the moreaerodynamically efficient regions of each of the plurality of blades108.

In a non-deployed state, such as during a high wind occurrence, whenloading/drag or thrust loads become too great for the rotor flapdeployable aerodynamic component 250 to withstand, the rotor flaps 256are retracted into the rotor blades 108, such as illustrated in FIGS. 23and 24. The aerodynamics of the rotor flap deployable aerodynamiccomponent 250 when in the non-deployed stated minimizes any blockage orredirecting of the flow of wind 112 and allows the wind 112 to flowtoward the inner portion 124 of the plurality of blades 108, asillustrated in FIG. 23.

FIGS. 25-29 illustrate a plurality of front views of a plurality ofembodiments of a deployable aerodynamic component 130, employing slidingpanel deployment features, and configured as a sliding panel deployableaerodynamic component 260. It should be understood that like featuresare designated with the same reference numbers throughout the figures.More specifically, FIGS. 25-29, illustrate embodiments of the deployableaerodynamic component 130 configured to couple to a wind turbine, suchas previously disclosed for the embodiments illustrated in FIGS. 1-24.In particular, illustrated in FIGS. 25 and 26 is an embodimentillustrating a front view of a front portion 262 including a pluralityof slideable panels 264, configured to align and misalign with aplurality of flow through openings 266 formed therein the sliding paneldeployable aerodynamic component 260. FIG. 25 illustrates the slidingpanel deployable aerodynamic component 260 in a deployed state. FIG. 26illustrates the sliding panel deployable aerodynamic component 260 in anon-deployed state. More particularly, the sliding panel deployableaerodynamic component 260 is configured having a plurality of slideablepanels 264 that slide relative to the front portion 262 so as to uncoverthe flow through openings 266 during non-deployment. Although thesliding panel deployable aerodynamic component 260 is illustrated havinga specific number of slideable panels 264, it should be understood thatthe component 260 may be configured to include any number of slideablepanels 264 dependent upon design parameters.

The sliding panel deployable aerodynamic component 260 is configured fordeployment by an actuation mechanism (not shown) utilizing hydraulics,levers, or the like to move the slideable panels 264 of the slidingpanel deployable aerodynamic component 260 to cover the flow throughopenings 266 in a manner to redirect an incoming wind 112 as illustratedin FIG. 25. During deployment, the slideable panels 264 are deployed ina manner to guide the wind toward the airfoiled shaped outer portion 122of the rotor blades 108 as previously described.

The sliding panel deployable aerodynamic component 260 is coupled to thewind turbine 100, and more particularly the hub 106 of the wind turbine100. In an embodiment the sliding panel deployable aerodynamic component260, and more particularly the front portion 262 may have a generalshape of a substantially spherical segment or a substantially paraboloidshape when viewed from a side, with a maximal outer diameter D of aboutthe diameter of a circle defined by the outer end of the inner portion(not shown) in operation of the wind turbine 100 when in a deployedstate.

The sliding panel deployable aerodynamic component 260 is deployable viamechanical automation that provides for sliding of the slideable panels264 to achieve deployment. The sliding of the panels 264 to cover orblock the flow through openings 266, as illustrated in FIG. 25, createsa dynamic structure in front of the plurality of rotor blades 108. Whendeployed, the sliding panel deployable aerodynamic component 260provides blockage and redirecting of the incoming wind 112 toward theouter portions 122 of each of the plurality of rotor blades 108, aspreviously described. In addition, the aerodynamic shape of the slidingpanel deployable aerodynamic component 260 causes an acceleration in theflow of wind 112 over the more aerodynamically efficient regions of eachof the plurality of blades 108.

In a non-deployed state, such as during a high wind occurrence, whenloading/drag or thrust loads become too great for the sliding paneldeployable aerodynamic component 260 to withstand, the slideable panels264 are mechanically actuated to slide and uncover the flow throughopenings 266, such as illustrated in FIG. 26, so as to allow the flow ofwind to pass therethrough. The aerodynamics of the sliding paneldeployable aerodynamic component 260 when in the non-deployed stateminimizes any blockage or redirecting of the flow of wind and allows thewind to flow toward the inner portion 124 of the plurality of blades108, as illustrated in FIG. 26.

Referring now to FIGS. 27-29, illustrated are additional configurationsfor the sliding panel deployable aerodynamic component 260. Moreparticularly, in contrast to the previous embodiment illustrated inFIGS. 25 and 26, the embodiments illustrated in FIGS. 27-29 include aplurality of slideable panels 264, but in this particular embodiment,the panels 264 are pie-shaped and slide or rotate about a central point272 and in an overlapping configuration when in a non-deployed state. Inparticular, illustrated in FIGS. 27-29 is an embodiment illustrating afront view of a front portion 262 including a plurality of slideablepanels 264, configured to slideably overlap so as to block or unblock aplurality of flow through openings 266. FIG. 27 illustrates the slidingpanel deployable aerodynamic component 260 in a deployed state. FIG. 28illustrates the sliding panel deployable aerodynamic component 260 in anon-deployed state. FIG. 29 illustrates an embodiment of the slidingpanel deployable aerodynamic component 260 including a support structure274 that may be configured to include an inner support ring 276, anouter support ring 278, or both.

The embodiments of the sliding panel deployable aerodynamic component260 illustrated in FIGS. 27-29 are configured having a plurality ofslideable panels 264 that slide relative to the each other so as to formthe flow through openings 266 during non-deployment. Although thesliding panel deployable aerodynamic component 260 is illustrated havinga specific number of slideable panels 264, it should be understood thatthe component 260 may be configured to include any number of slideablepanels 264 dependent upon design parameters.

The sliding panel deployable aerodynamic component 260 is configured fordeployment by an actuation mechanism (not shown) utilizing hydraulics,levers, or the like to move the slideable panels 264 of the slidingpanel deployable aerodynamic component 260 to cover the flow throughopenings 266 in a manner to redirect an incoming wind 112 as illustratedin FIG. 27. During deployment, the slideable panels 264 are deployed ina manner to guide the wind 112 toward the airfoiled shaped outer portionof the rotor blades as previously described.

The sliding panel deployable aerodynamic component 260 is coupled to thewind turbine (not shown), and more particularly the hub (not shown) ofthe wind turbine. In an embodiment the sliding panel deployableaerodynamic component 260, and more particularly the front portion 262may have a general shape of a substantially spherical segment or asubstantially paraboloid shape with a maximal outer diameter D of aboutthe diameter of a circle defined by the outer end of the inner portionin operation of the wind turbine when in a deployed state.

Similar to the previously disclosed sliding panel embodiment, thesliding panels 264 are deployable via mechanical automation thatprovides for sliding of the slideable panels 264 to achieve deployment.The sliding of the panels 264 creates a dynamic structure in front ofthe plurality of rotor blades 108. When deployed, the sliding paneldeployable aerodynamic component 260 provides blockage and redirectingof the incoming wind 112 toward the outer portions 122 of each of theplurality of rotor blades 108, as previously described. In addition, theaerodynamic shape of the sliding panel deployable aerodynamic component260 causes an acceleration in the flow of wind 112 over the moreaerodynamically efficient regions of each of the plurality of blades108.

In a non-deployed state, such as during a high wind occurrence, whenloading/drag or thrust loads become too great for the sliding paneldeployable aerodynamic component 260 to withstand, the slideable panels264 are mechanically actuated to slide and form the flow throughopenings 266, such as illustrated in FIGS. 28 and 29. The aerodynamicsof the sliding panel deployable aerodynamic component 260 when in thenon-deployed stated minimizes any blockage or redirecting of the flow ofwind 112 and allows the wind 112 to flow toward the inner portion 124 ofthe plurality of blades 108.

In FIG. 30 a method for aerodynamic performance enhancement of a windturbine, thus improving the efficiency of an existing wind turbine isshown at 300. In a first step 302, a wind turbine is provided. The windturbine includes a hub and at least one rotor blade connected to thehub. The at least one rotor blade has an inner portion and a profiledouter portion as previously described here-above. Next, in step 304, adeployable aerodynamic component is mounted on the hub. The deployableaerodynamic component may be one of the deployable aerodynamiccomponents described here-above. In a further step 306, a determinationis made as to the presence of winds exceeding preset parameters. If windexceed preset parameters, the deployable aerodynamic component operatesin a non-deployed state, at step 308, to allow the incoming wind to passtherethrough toward an inner portion of the at least one rotor blade. Ifwind does not exceed preset parameters, the deployable aerodynamiccomponent is deployed to redirect an incoming wind toward a profiledouter portion of the at least one rotor blade, at step 310 and provideincreased efficiency and enhanced aerodynamic performance of the windturbine. At a step 312, the wind turbine is operated by rotating the atleast one rotor blade about its longitudinal axis to generate energy.Step 306 is repeated during operation of the wind turbine to determinethe need commence or cease deployment of the deployable aerodynamiccomponent as described in steps 308 and 310.

Disclosed is a deployable aerodynamic component for enhanced aerodynamicperformance of a wind turbine. The deployable aerodynamic componenthaving dimensions such that the air impinging the wind turbine at theinner rotor diameter will be guided to profiled rotor blade portions andthus will increase the energy capture of the wind turbine. In a typicalembodiment of the deployable aerodynamic component the outer dimensionsof the nacelle may be adapted to the deployable aerodynamic component toincrease energy capture and to avoid vortex in the down flow windstream. Therefore the energy capture is increased, and less energy isloss as the air stream at the inner rotor diameter is guided to theprofiled rotor blade portions.

The deployable aerodynamic component may be fabricated of any suitablematerial including, but not limited to stretchable fabric, tensionablefabric, plastic, metal, carbon fiber and/or other construction material.In an embodiment of the deployable aerodynamic component including anunderlying support structure, the structure may be fabricated of anysuitable material, including, but not limited to carbon fiber and/orother material capable of lending support to the deployable aerodynamiccomponent. In addition, as disclosed here-above, the deployableaerodynamic component may be configured to operate solely when spinningwith the rotor blades, such as the weighted cable deployable aerodynamiccomponent 180 described with regard to FIGS. 8-11. In an alternativeembodiment, the deployable aerodynamic component may be configured tospin or remain stationary relative to the rotor blades, and is notdependent upon a rotational force to deploy. Embodiments disclosedherein include a deployable aerodynamic component having a substantiallydome-shaped configuration when deployed. In alternate embodiments, thedome may not be a full 360 degrees, and may be configured having a“shroud-like” shape to direct the incoming wind in an upward and outwarddirection toward the airfoiled shaped outer portion of the rotor bladesand/or to substantially cover each of the plurality of blades only.

Accordingly, disclosed is an apparatus and method for aerodynamicperformance enhancement of a wind turbine configured to operate in adeployed state to redirect an incoming wind toward a profiled outerportion of the at least one rotor blade and in a non-deployed state toallow the incoming wind to pass therethrough toward the inner portion ofthe at least one rotor blade. It will be understood that the previousapparatus configurations and modes of operation described herein aremerely examples of proposed apparatus configurations and operatingconditions. What is significant is the apparatus provides for enhancedaerodynamic performance and thus increased efficiency of a wind turbine.

The foregoing has described an apparatus and method for aerodynamicperformance enhancement of a wind turbine. While the present disclosurehas been described with respect to a limited number of embodiments,those skilled in the art, having benefit of this disclosure, willappreciate that other embodiments may be devised which do not departfrom the scope of the disclosure as described herein. While the presentdisclosure has been described with reference to exemplary embodiments,it will be understood by those skilled in the art that various changesmay be made and equivalents may be substituted for elements thereofwithout departing from the scope of the disclosure. In addition, manymodifications may be made to adapt a particular situation or material tothe teachings of the present disclosure without departing from theessential scope thereof. Therefore, it is intended that the presentdisclosure not be limited to the particular embodiment disclosed as thebest mode contemplated for carrying out the disclosure. It is,therefore, to be understood that the appended claims are intended tocover all such modifications and changes as fall within the true spiritof the disclosure.

1. An aerodynamic component for a wind turbine configured to be mountedto said wind turbine, wherein at least one rotor blade is connected to ahub of said wind turbine and defines an inner portion and a profiledouter portion, the aerodynamic component comprising: a front portionconfigured to be positioned in front of the inner portion of the atleast one rotor blade of the wind turbine in operation; wherein theaerodynamic component is structurally configured to: operate in adeployed state to redirect an incoming wind toward the profiled outerportion of the at least one rotor blade; operate in a non-deployed stateto allow the incoming wind to pass therethrough toward the inner portionof the at least one rotor blade; and allow rotation of the at least onerotor blade about its longitudinal axis for pitch angle adjustment ofthe at least one rotor blade without interfering with the deployment ofthe aerodynamic component.
 2. The aerodynamic component according toclaim 1, wherein in a side view, the aerodynamic component has adeployed shape of a substantially spherical segment.
 3. The aerodynamiccomponent according to claim 1, wherein in a side view the aerodynamiccomponent has a substantially paraboloidal shape.
 4. The aerodynamiccomponent according to claim 1, wherein the aerodynamic component is aroller and support arc deployable aerodynamic component.
 5. Theaerodynamic component according to claim 1, wherein the aerodynamiccomponent is an umbrella-like deployable aerodynamic component
 6. Theaerodynamic component according to claim 1, wherein the aerodynamiccomponent is a weighted cable deployable aerodynamic component.
 7. Theaerodynamic component according to claim 1, wherein the aerodynamiccomponent is a fluid deployable aerodynamic component.
 8. Theaerodynamic component according to claim 1, wherein the aerodynamiccomponent is a perimeter paneled deployable aerodynamic component. 9.The aerodynamic component according to claim 1, wherein the aerodynamiccomponent is a paneled deployable aerodynamic component.
 10. Theaerodynamic component according to claim 1, wherein the aerodynamiccomponent is a rotor flap deployable aerodynamic component.
 11. Theaerodynamic component according to claim 1, wherein the aerodynamiccomponent is a slideable panel deployable aerodynamic component.
 12. Awind turbine comprising: a hub; at least one rotor blade connected tothe hub, the rotor blade comprising an inner portion and a profiledouter portion; and a deployable aerodynamic component configured to bemounted to the wind turbine, the deployable aerodynamic componentcomprising: a front portion configured to be positioned in front of theinner portion of the at least one rotor blade of the wind turbine inoperation; wherein the deployable aerodynamic component is structurallyconfigured to: operate in a deployed state to redirect an incoming windtoward the profiled outer portion of the at least one rotor blade;operate in a non-deployed state to allow the incoming wind to passtherethrough toward the inner portion of the at least one rotor blade;and allow rotation of the at least one rotor blade about itslongitudinal axis for pitch angle adjustment of the at least one rotorblade without interfering with the deployment of the aerodynamiccomponent.
 13. The wind turbine according to claim 12, wherein thedeployable aerodynamic component has a shape of one of a substantiallyspherical segment or a paraboloidal shape.
 14. The wind turbineaccording to claim 12, wherein the deployable aerodynamic component isan umbrella-like deployable aerodynamic component
 15. The wind turbineaccording to claim 12, wherein the deployable aerodynamic component is aweighted cable deployable aerodynamic component.
 16. The wind turbineaccording to claim 12, wherein the deployable aerodynamic component is afluid deployable aerodynamic component.
 17. The wind turbine accordingto claim 12, wherein the deployable aerodynamic component is a paneleddeployable aerodynamic component.
 18. The wind turbine according toclaim 12, wherein the deployable aerodynamic component is a rotor flapdeployable aerodynamic component.
 19. A method for aerodynamicperformance enhancement of a wind turbine comprising: providing a windturbine including a hub and at least one rotor blade connected to thehub, the at least one rotor blade having an inner portion and a profiledouter portion; mounting a deployable aerodynamic component to the windturbine; determining the presence of winds exceeding preset parameters;deploying the deployable aerodynamic component to redirect an incomingwind toward the profiled outer portion of the at least one rotor bladewhen winds do not exceed the present parameters and operating thedeployable aerodynamic component in a non-deployed state to allow theincoming wind to pass therethrough toward the inner portion of the atleast one rotor blade when winds exceed the present parameters; androtating the at least one rotor blade about its longitudinal axis togenerate energy.
 20. The method according to claim 19, wherein thedeployable aerodynamic component has a shape of one of a substantiallyspherical segment or a paraboloidal shape.